An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.

A turbocharged compressor system using an Organic Rankine Cycle system to recover waste heat from a compression process. The Organic Rankine Cycle system circulates an organic fluid through an evaporator, where the organic fluid vaporizes and is expanded in a turbine section of a turbocharger to drive a compressor section of the turbocharger. The organic fluid vapor is condensed in a condenser and is pumped to the evaporator once again for recirculation. The compressor section of the turbocharger pre-compresses a working fluid before entering an airend in a compression system. As the working fluid exits the airend, it may be delivered to the evaporator, where the waste heat from the working fluid evaporates the organic fluid flowing in the Organic Rankine Cycle system. The working fluid may also be circulated between intercoolers in multi-stage compressor systems.

A turbocharged compressor system using an Organic Rankine Cycle system to recover waste heat from a compression process. The Organic Rankine Cycle system circulates an organic fluid through an evaporator, where the organic fluid vaporizes and is expanded in a turbine section of a turbocharger to drive a compressor section of the turbocharger. The organic fluid vapor is condensed in a condenser and is pumped to the evaporator once again for recirculation. The compressor section of the turbocharger pre-compresses a working fluid before entering an airend in a compression system. As the working fluid exits the airend, it may be delivered to the evaporator, where the waste heat from the working fluid evaporates the organic fluid flowing in the Organic Rankine Cycle system. The working fluid may also be circulated between intercoolers in multi-stage compressor systems.

The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).

A jet engine is provided having a front compression stage for pressurizing intake air, and a central superheating section for further increasing the temperature and pressure of the pressurized intake air from the front compression stage. The central superheating section is at least partially electrically powered by an internal energy generating power source. A rear exhaust nozzle stage recovers energy from a discharge of the superheating section and creates thrust.

A jet engine is provided having a front compression stage for pressurizing intake air, and a central superheating section for further increasing the temperature and pressure of the pressurized intake air from the front compression stage. The central superheating section is at least partially electrically powered by an internal energy generating power source. A rear exhaust nozzle stage recovers energy from a discharge of the superheating section and creates thrust.

A pressure zoned spraybar for an augmentor section of a gas turbine engine may comprise a fuel conduit and a pressure valve in fluid communication with the fuel conduit. A fuel nozzle may be downstream of the pressure valve. The pressure valve may be configured to regulate a flow of fluid to the fuel nozzle.

A pressure zoned spraybar for an augmentor section of a gas turbine engine may comprise a fuel conduit and a pressure valve in fluid communication with the fuel conduit. A fuel nozzle may be downstream of the pressure valve. The pressure valve may be configured to regulate a flow of fluid to the fuel nozzle.

A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.

A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.